56856 Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations 

Instructions of Airbus Service Bulletin A320–

25–1394, Revision 01, dated December 12, 

2005. If the stiff part of the girt or the girt bar 

position is incorrect, before further flight, 

repair in accordance with the service 

bulletin. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

(g) Inspecting and repairing if necessary 

before the effective date of this AD in 

accordance with Airbus Service Bulletin 

A320–25–1394, dated July 23, 2004, is 

acceptable for compliance with the 

requirements of paragraph (f) of this AD. 

Credit for AD 2005–23–05, Amendment 39–

14363 

(h) Accomplishing the actions required by 

paragraph (g) of AD 2005–23–05 is acceptable 

for compliance with the corresponding 

requirements of paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(j) French airworthiness directive F–2005–

172, issued December 21, 2005, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(k) You must use Airbus Service Bulletin 

A320–25–1394, Revision 01, dated December 

12, 2005, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, for a 

copy of this service information. You may 

review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street, SW., Room PL–401, 

Nassif Building, Washington, DC; on the 

Internet at http://dms.dot.gov; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the NARA, 

call (202) 741–6030, or go to http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 14, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–8229 Filed 9–27–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24867; Directorate 

Identifier 2006–NM–064–AD; Amendment 

39–14773; AD 2006–20–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–102, –103, and –106 

Airplanes, and Model DHC–8–200 and 

DHC–8–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bombardier Model DHC–8–102, –103, 

and –106 airplanes, and Model DHC–8–

200 and DHC–8–300 series airplanes. 

This AD requires performing a one-time 

general visual inspection for nonconforming chain links of chain 

assemblies of the elevator trim system 

and gust lock system, and corrective 

actions if necessary. This AD also 

requires temporary revisions to the 

airplane flight manuals of the affected 

airplanes, which describe procedures 

for elevator trim checks. This AD results 

from reports of several failures of the 

elevator trim chain, due to hydrogen 

embrittlement. We are issuing this AD 

to prevent breakage of the elevator trim 

chain, which would prevent the actual 

position of the elevator trim tab from 

being annunciated to the flightcrew. 

Attempting to adjust the trim tab from 

the full nose up or full nose down 

position with a broken trim chain could 

result in misleading information relative 

to takeoff trim settings and consequent 

loss of control on takeoff. 

DATES: This AD becomes effective 

November 2, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 2, 2006. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Bombardier, Inc., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 

1Y5, Canada, for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Ezra 

Sasson, Aerospace Engineer, Systems 

and Flight Test Branch, ANE–172, FAA, 

New York Aircraft Certification Office, 

1600 Stewart Avenue, suite 410, 

Westbury, New York 11590; telephone 

(516) 228–7320; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Bombardier Model 

DHC–8–102, –103, and –106 airplanes, 

and Model DHC–8–200 and DHC–8–300 

series airplanes. That NPRM was 

published in the Federal Register on 

May 25, 2006 (71 FR 30070). That 

NPRM proposed to require performing a 

one-time inspection for non-conforming 

chain links of chain assemblies of the 

elevator trim system and gust lock 

system, and corrective actions if 

necessary. That NPRM also proposed to 

require temporary revisions to the 

airplane flight manuals of the affected 

airplanes, which describe procedures 

for elevator trim checks. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the single comment 

received. 

Request To Revise Costs of Compliance 

One commenter, Horizon Air, 

requests that we adjust the costs of 

compliance in the NPRM. Horizon Air 

asserts that, rather than the 5 work 

hours specified in the NPRM to 

accomplish the inspection on each 

airplane, the figure specified by 

Bombardier of 15 work hours to 


jlentini on PROD1PC65 with RULES
Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations 56857 

accomplish the inspection is far more 

relevant. Further, Horizon Air states that 

all chain link assemblies will likely 

need to be replaced on its airplanes and 

asserts that, according to Bombardier, an 

additional 32 work hours per airplane 

would be needed to replace the 

assemblies. Horizon Air believes the 

costs of compliance will far exceed the 

estimated figure of $400 per airplane 

specified in the NPRM. 

We do not agree. The economic 

analysis of an AD is limited to the cost 

of actions that are actually required. The 

economic analysis does not consider the 

costs of on-condition actions, such as 

repairing a crack detected during a 

required inspection (‘‘repair, if 

necessary’’). Such on-condition repairs 

would be required—regardless of AD 

direction—to correct an unsafe 

condition identified in an airplane and 

to ensure that the airplane is operated 

in an airworthy condition, as required 

by the Federal Aviation Regulations. We 

have not changed the AD in this regard. 

Clarification of Type of Inspection 

We specified a ‘‘general visual 

inspection’’ in the NPRM to eliminate 

any confusion about the proper type of 

inspection; however, we neglected to 

include a definition of this type of 

inspection in the NPRM. Therefore, we 

added Note 2 to the AD to define a 

general visual inspection. 

Clarification of End-Level Effect 

We have determined that the 

description in the NPRM of the endlevel effect of the unsafe condition is 

not entirely accurate. Therefore, we 

have revised the AD to more clearly 

describe the probable end-level effect of 

the unsafe condition on the airplane. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

This AD affects about 166 airplanes of 

U.S. registry. The required inspection 

will take about 5 work hours per 

airplane, at an average labor rate of $80 

per work hour. Based on these figures, 

the estimated cost of the required 

inspection for U.S. operators is $66,400, 

or $400 per airplane. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2006–20–04 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–14773. 

Docket No. FAA–2006–24867; 

Directorate Identifier 2006–NM–064–AD. 

Effective Date 

(a) This AD becomes effective November 2, 

2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–102, –103, and –106 airplanes, and 

Model DHC–8–200 and DHC–8–300 series 

airplanes, certificated in any category; as 

identified in Bombardier Service Bulletin 8–

27–105, Revision A, dated September 13, 

2005. 

Unsafe Condition 

(d) This AD results from reports of several 

failures of the elevator trim chain, due to 

hydrogen embrittlement. We are issuing this 

AD to prevent breakage of the elevator trim 

chain, which would prevent the actual 

position of the elevator trim tab from being 

annunciated to the flightcrew. Attempting to 

adjust the trim tab from the full nose up or 

full nose down position with a broken trim 

chain could result in misleading information 

relative to takeoff trim settings and 

consequent loss of control on takeoff. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Temporary Amendments (TAs) 

(f) Within 30 days after the effective date 

of this AD, revise the applicable airplane 

flight manual (AFM) of the affected airplanes 

by incorporating the information in the 

applicable TAs into the AFMs listed in Table 

1 of this AD. This may be accomplished by 

inserting a copy of the applicable TA into the 

AFM. The copy of the TA may be removed 

from the AFM when a new revision of the 

AFM is released that incorporates material 

identical to the content of the TA. 


jlentini on PROD1PC65 with RULES
56858 Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations 

TABLE 1.—DE HAVILLAND TAS

For airplane model— 

Use de 

Havilland TA 

No.— 

Dated— To the de Havilland Dash 8 Model— 

102 ................................................. 9 January 28, 2004 ... 102 Flight Manual PSM 1–81–1A. 

102NS ............................................ 8 January 28, 2004 ... 102 NS Flight Manual PSM 1–81–1A. 

103 ................................................. 9 January 28, 2004 ... 103 Flight Manual PSM 1–81–1A. 

103NS ............................................ 8 January 28, 2004 ... 103 NS Flight Manual PSM 1–81–1A. 

106 ................................................. 9 January 28, 2004 ... 106 Flight Manual PSM 1–81–1A. 

106NS ............................................ 8 January 28, 2004 ... 106 NS Flight Manual PSM 1–81–1A. 

201 ................................................. 11 June 22, 2005 ........ 201 Flight Manual PSM 1–82–1A. 

201S ............................................... 9 June 22, 2005 ........ 201 S Flight Manual PSM 1–82–1A. 

202 ................................................. 10 January 28, 2004 ... 202 Flight Manual PSM 1–82–1A. 

202HT ............................................. 8 January 28, 2004 ... 202 HT Flight Manual PSM 1–82–1A. 

202S ............................................... 9 June 22, 2005 ........ 202 S Flight Manual PSM 1–82–1A. 

301 ................................................. 8 January 28, 2004 ... 301 Flight Manual PSM 1–83–1A. 

311 ................................................. 15 January 28, 2004 ... 311 Flight Manual PSM 1–83–1A. 

315 ................................................. 9 January 28, 2004 ... 315 Flight Manual PSM 1–83–1A. 

Note 1: The suffixes ‘‘NS,’’ ‘‘S,’’ and ‘‘HT,’’

do not indicate separate airplane models; for 

example, a Model 102NS airplane is a Model 

102 airplane. 

Inspection and Corrective Actions 

(g) Within 6,000 flight hours or 36 months 

after the effective date of this AD, whichever 

occurs first, perform a one-time general 

visual inspection for non-conforming chain 

links of the trim chain/chain assemblies of 

the elevator trim system and gust lock system 

and, before further flight, do the applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–27–105, Revision A, dated 

September 13, 2005. After accomplishing the 

requirements of this paragraph, operators 

may remove the AFM revisions required by 

paragraph (f) of this AD from the AFM. 

Note 2: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Parts Installation 

(h) As of the effective date of this AD, no 

person may install an elevator trim chain/ 

chain assembly on any airplane, unless the 

chain links of that trim chain/chain assembly 

are identified with the number RC–25. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, New York Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(j) Canadian airworthiness directive CF–

2005–38, dated October 25, 2005, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(k) You must use Bombardier Service 

Bulletin 8–27–105, Revision A, dated 

September 13, 2005, and the temporary 

amendments specified in Table 2 of this AD, 

as applicable, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of these documents in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Bombardier, Inc., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 1Y5, 

Canada, for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street, SW., Room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 2.—TEMPORARY AMENDMENTS INCORPORATED BY REFERENCE

de Havilland temporary amendment— Dated— To the de Havilland Dash 8 Model— 

8 ............................................................................ January 28, 2004 ................................................. 102 NS Flight Manual PSM 1–81–1A. 

8 ............................................................................ January 28, 2004 ................................................. 103 NS Flight Manual PSM 1–81–1A. 

8 ............................................................................ January 28, 2004 ................................................. 106 NS Flight Manual PSM 1–81–1A. 

8 ............................................................................ January 28, 2004 ................................................. 202 HT Flight Manual PSM 1–82–1A. 

8 ............................................................................ January 28, 2004 ................................................. 301 Flight Manual PSM 1–83–1A. 

9 ............................................................................ January 28, 2004 ................................................. 102 Flight Manual PSM 1–81–1A. 

9 ............................................................................ January 28, 2004 ................................................. 103 Flight Manual PSM 1–81–1A. 

9 ............................................................................ January 28, 2004 ................................................. 106 Flight Manual PSM 1–81–1A. 

9 ............................................................................ June 22, 2005 ...................................................... 201 S Flight Manual PSM 1–82–1A. 

9 ............................................................................ June 22, 2005 ...................................................... 202 S Flight Manual PSM 1–82–1A. 

9 ............................................................................ January 28, 2004 ................................................. 315 Flight Manual PSM 1–83–1A. 

10 .......................................................................... January 28, 2004 ................................................. 202 Flight Manual PSM 1–82–1A. 

11 .......................................................................... June 22, 2005 ...................................................... 201 Flight Manual PSM 1–82–1A. 

15 .......................................................................... January 28, 2004 ................................................. 311 Flight Manual PSM 1–83–1A. 


jlentini on PROD1PC65 with RULES
Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations 56859 

Issued in Renton, Washington, on 

September 14, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–8226 Filed 9–27–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22974; Directorate 

Identifier 2005–NM–180–AD; Amendment 

39–14774; AD 2006–20–05] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

BAe 146 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

BAE Systems (Operations) Limited 

Model BAe 146 airplanes. This AD 

requires repetitive inspections to 

measure the depth of chafing or scoring 

in the skin along the full length of the 

wing-to-fuselage fairing from forward to 

aft ends at the contact between the seal 

and fuselage, and related investigative/ 

corrective actions if necessary. This AD 

results from a report of chafing in this 

area. We are issuing this AD to detect 

and correct such chafing or scoring, 

which could result in reduced structural 

integrity of the fuselage. 

DATES: This AD becomes effective 

November 2, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 2, 2006. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact British Aerospace Regional 

Aircraft American Support, 13850 

Mclearen Road, Herndon, Virginia 

20171, for service information identified 

in this AD. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the street 

address stated in the ADDRESSES section. 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that would apply to certain BAE 

Systems (Operations) Limited Model 

BAe 146 airplanes. That supplemental 

NPRM was published in the Federal 

Register on April 5, 2006 (71 FR 17037). 

That supplemental NPRM proposed to 

require repetitive inspections to 

measure the depth of chafing or scoring 

in the skin along the full length of the 

wing-to-fuselage fairing from forward to 

aft ends at the contact between the seal 

and fuselage, and related investigative/ 

corrective actions if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment we received on 

the supplemental NPRM. 

Request for Revised Compliance Time 

BAE notes that corresponding British 

airworthiness directive G–2005–0020, 

dated July 6, 2005, allows an additional 

4,000 flight cycles before previously 

inspected airplanes must be 

reinspected. But paragraph (f) of the 

supplemental NPRM would require all 

airplanes to be inspected before the 

airplane accumulates 1,000 total flight 

cycles, or within a grace period of 500 

flight cycles, without any provision for 

an extended compliance time for 

airplanes previously inspected in 

accordance with both BAE Systems 

(Operations) Limited Inspection Service 

Bulletins ISB.53–005, Revision 2, dated 

February 16, 2005, and ISB.53–067, 

Revision 3, dated June 27, 2005. BAE 

adds that there are no airplanes in 

service with fewer than 1,000 total flight 

cycles. 

We infer that the commenter requests 

that we revise the supplemental NPRM. 

We agree. We have revised paragraph (f) 

to allow the deferral of certain 

corrective actions under specific 

conditions outlined in the service 

bulletins, as provided in new paragraph 

(h) in this AD. 

Additional Changes to Supplemental 

NPRM 

The supplemental NPRM specified 

that all actions including corrective 

actions would be required at the times 

specified in BAE Systems (Operations) 

Limited Inspection Service Bulletins 

ISB.53–005 and ISB.53–067. Our intent 

was to match the specifications of the 

service bulletins, which allow deferred 

corrective action only under certain 

conditions. To clarify the required 

compliance times of this AD, we have 

added new paragraph (h) to explicitly 

require corrective actions before further 

flight, except when repair may be 

deferred under the specific conditions 

noted in the service bulletins. 

Paragraph (g) of the supplemental 

NPRM specified making repairs using a 

method approved by either the FAA or 

the Civil Aviation Authority, which is 

the airworthiness authority for the 

United Kingdom. The European 

Aviation Safety Agency (EASA) has 

assumed responsibility for the airplane 

model subject to this AD. Therefore, we 

have revised paragraph (g) of this AD to 

specify making repairs using a method 

approved by the FAA, the CAA (or its 

delegated agent), or the EASA (or its 

delegated agent). 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 


jlentini on PROD1PC65 with RULES